Fundamental investigation using active plasma control to reduce blade–vortex interaction noise

Patel, Trushant K.; Lilley, Alexander J.; Shen, Weiqi; Porrello, Christian; Schindler-Tyka, A.; Roy, Subrata; Lear, W. E.; Miller, Steven A.

doi:10.1177/1475472x211052699

Cited by 8 publications

(5 citation statements)

References 41 publications

(54 reference statements)

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“…Many studies have shown the potential use of plasma actuators as flow control devices across a wide range of flow applications. Examples include control of transition to turbulence [8][9][10], drag reduction for highway vehicles [11][12][13], lift to drag ratio modification for flow over a wing [14,15], flow modification over bluff bodies [13,16], blade vortex interaction noise control [17], flight control for small aircrafts and projectiles [18,19] and deicing application [20][21][22]. However, environmental ruggedness and performance reliability of these actuators must be studied before their practical implementation for any external flow applications.…”

Section: Introductionmentioning

confidence: 99%

Performance recovery of plasma actuators in wet conditions

Lilley¹,

Roy²,

Michels³

et al. 2022

J. Phys. D: Appl. Phys.

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Plasma actuators have been extensively studied for flow control applications. While these studies have been traditionally focused on characterizing their performances as flow control devices, the performance of plasma actuators under adverse conditions like light rain remains to be less explored. This paper seeks to study the effects of water adhesion from droplets directly sprayed on to a plasma actuator using thrust recovery as the performance metric. It was found in all tests that wet actuators quickly recover plasma glow, before gradually regaining performance comparable to the dry actuator. The measured thrust for the wet actuator after 5 seconds of operation recovered by 46% and 42% of the thrust of the dry actuator for 50.0-62.5 g/m2 and 125-150 g/m2 of sprayed water droplets, respectively. At 22.5 kVpp and 14 kHz, the highest thrust recovery was recorded at 84% of that of the dry actuator after 80 seconds of operation. For 17.5 kVpp and 14 kHz the wet thrust recovered by 79%, while for 22.5 kVpp and 10 kHz the wet thrust recovered by 68% of their dry counterpart in 80 seconds. For 17.5 kVpp and 14 kHz, the thrust almost fully recovered in comparison to the dry actuator after about 290 seconds of operation. These results indicate that both applied voltage and operating frequency plays a critical role in the performance recovery while the latter may have a stronger influence. Performance recovery for a wet serpentine shaped plasma actuator is also included for general applicability. The power data in all cases show that wet actuators consume more power which with time gradually approach the dry actuator power data. This because during the initial stages of operation, the rolling mean current of the wet actuator is higher than the dry actuator even though the ionization spikes of dry actuator is stronger.

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Section: Introductionmentioning

confidence: 99%

Performance recovery of plasma actuators in wet conditions

Lilley¹,

Roy²,

Michels³

et al. 2022

J. Phys. D: Appl. Phys.

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“…From figure 17, the actuator on case with sinusoidal waveform has significant delay in dynamic stall when compared to actuator off case (figure 16). During the upstroke there is no dynamic stall vortex formation or flow reversal in comparison to actuator off (figures 16,17). At α = 20°, the actuator on case has a region of flow reversal near the trailing edge (figure 17), while the actuator off case has flow reversal over the entire chord length (figure 16).…”

Section: Actuator On St F = 50 Sinusoidal Waveformmentioning

confidence: 99%

“…Plasma actuators, specifically surface dielectric barrier discharge (SDBD) actuators, are surface-compliant electrical devices that can impart momentum into the neighboring fluid through ionization of the local medium inducing Lorentz body force [12]. Despite the small momentum input, plasma actuators have been proposed for a wide variety of uses ranging from aircraft stall control [13,14], deicing [15,16], noise reduction [17], drag reduction [18], tandem airfoil interaction [19], flow mixing enhancement [20], microbial sterilization [21,22] to food preservation [23]. Studies have shown that even though plasma actuators' performance degrade under certain environmental conditions such as excessive humidity [24][25][26], they can be designed to operate in icy [15,16] and wet conditions [27], although this are remains largely unexplored.…”

Section: Introductionmentioning

confidence: 99%

Novel plasma actuator for mitigation of dynamic stall

Lilley,

Roy,

Visbal

2024

Phys. Scr.

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A novel plasma actuator, the Linear Counter-flow using a Point Embedded Electrode (LCPEE), is developed for the prevention of dynamic stall for a sinusoidal pitching movement between α = 4° and α = 18°. The LCPEE is implemented on a NACA0012 airfoil at a Reynolds Number of Rec = 2 × 105 and reduced frequency of k = π/16. For prior investigations using a standard linear actuator, the exposed electrode introduces perturbations passively which delay dynamic stall when the actuator is off. For the LCPEE actuator, when turned off, there is minor passive delay. When the LCPEE is turned on at Stf = 50, dynamic stall is prevented for the motion. The LCPEE actuator is also tested for the same sinusoidal motion but between α = 6° and α = 20°. Four cases are considered for the higher range of motion: actuator off, actuator on Stf = 50 sinusoidal input waveform, actuator on Stf = 50 triangular input waveform, and actuator on Stf = 100 sinusoidal input waveform. For actuator on Stf = 100 sinusoidal input waveform case, no flow reversal is present.

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“…Plasma flow control is a novel flow control method developed in recent years, which plays an important role in improving the performance of various fluid machinery [3], including controlling boundary layer [4], delaying airflow separation [5], which usually leads to the augmentation of lift and the decreasing drag, suppression of aerodynamic noise [6], aeroelastic control [7], and controlling wingtip vortex [8]. Popular plasma actuators include plasma synthetic jet actuator and dielectric barrier discharge (DBD) plasma actuator (PA) and this paper focuses on the latter.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of virtual control surfaces for lift control on NACA0015 airfoil

Fu,

Lyu,

Shi

2023

Phys. Scr.

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The plasma actuators as virtual control surfaces are assessed numerically as a means to control the lift of NACA0015 airfoil at the full angle of attack (without stall). The virtual control surface for increasing lift is realized by the pressure side (PS) plasma actuators that induce an upstream jet and the suction side (SS) plasma actuators that induce a downstream jet (SSD plasma actuator), while the one for reducing lift is realized by the SS plasma actuators that induce an upstream jet (SSU plasma actuator). Numerical simulation is achieved by solving the two-dimensional Reynolds averaged Navier-Stokes using the finite volume method. The plasma actuator adopts the empirical model proposed by the author before. The simulation of the air flow was performed for the freestream velocity of 20 m/s (Re=$1.03\times 10^6$) and the induced jet momentum coefficient between 0.0846\% and 0.9027\%. The calculation results show that the optimal number of DBD actuators for increasing the lift is related to the angle of attack. The SS flow separation of the high angle of attack greatly reduces the control effect of the PS actuator, which can be eliminated by arranging the actuators in front of the separation point. Finally, a virtual control surfaces configuration containing three groups of seven plasma actuators is obtained.

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Fundamental investigation using active plasma control to reduce blade–vortex interaction noise

Cited by 8 publications

References 41 publications

Performance recovery of plasma actuators in wet conditions

Performance recovery of plasma actuators in wet conditions

Novel plasma actuator for mitigation of dynamic stall

Numerical investigation of virtual control surfaces for lift control on NACA0015 airfoil

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